US2647730A - Oil cooler protective means - Google Patents

Description

g- 4, 1953 w. D. TEAGUE, JR 2,647,730

1 OIL COOLER PROTECTIVE MEANS Filed July 22, 1949 FIG. 1

T0 ENGINE FROM SUMP

T0 ENGINE HN'ORA/EV y||fij INVENTOR.

\ T 'WALTER D. T EAGUE JR.

Patented Aug. 4, 1953 UNITED sures PATENT OFFICE 61L edema MEA NS Walter 'D. Teague, Jr., Alpine,

'BendiaAy atmn- Qo a i n,

N. J.', assignor .to Teterb'oro, N. 'J.,

a corporation of Delaware Afiiflidfidfi .my'zz, 1949, serial in. 106,222

Claiihs;

The present invention relates to means for protesting the oil supply in an engine. t v

, The protective means herein disclosed. fimlparticular utile application in military aircraft in;- t l q here n Ii d re t. it an he. ngine rad ato While nsufficient o dis b e., he-.. c aft night still cause disaster due to the complete loss of the oilsu-pply,

It is known in that an aircraft can efiectively cruise tor a; great-. distance and for a r' rq nee rl id e m With t t e nemevo circulating thr oujgh the radiator, i or altho ugh under; these conditions the oil. will over-heat and rose effectiveness, lubrication w1'11 still the present, and a considerabletin e wi ll elapse beio'rethe oil heats to a.

t e; a

p t Qt o eleite br'ce det'm- T ims u fai i rab e b nq t bn a t r mi iea ed b I he t e O l t l ,br i e se th .1? e,

the oil system fact that as v sump and other components of hegjin functioning as radiators since the heat transfer from. the over-heated on to" these comii tl ilt s idl awelm i 1 I v a t th ri qr'a re l f r th qmfttq- @9 time u ti in f l-fa en t 9i t me and thereby, enable the beware to reaoh a friendly base or, at least, select a site; for an emergency ending.

i, It; is) many weir known in the, at

that without'oil supply .whatsoever the engine th iad'iatorin the event of a hit the v reori BS1 a ilet p fie m s ile s ain another cit es. k, l prdvi wh b li i a u c m ans w ll. ai seri ineq b as theradiator and a}; e the operates simulaiiequ i o ti e. .Q L

t l ano her 'l t P li ride pretective means we; w en? i lbe t ea I to insta I, yet po's further bi iiifotectiye niean will triil of time, thereby forcing an immediate or electrical V The roregmgand other objects and advantages will appear more fully hereinafter from a consideration of the tailedde'scription which follows, taken together 'with the accompanying drawing, wherein two embodiments of theiriirention are illustrated by way of example.- lit. is to beek'pre'ssly understood, however; that them-awing is for the purposes of illustration only, and. is "not to be construed as defining the limits of the invention, reference being had fer this purpose to the appended claims.

In the drawing wherein aster designate likesp'artsz l Figure 1 is a diagram of the system partly in schematic. v v

Figure 2- is a, scher'natic diagram showingan alternate embodiment of. the invention-1 Referring now to the drawing, andm'oreparticui'arly to Figure 1', an engine oil. radiator gen! erally' designated:

like reference char by the numeral I10 contains oil inlet l2 an'dvoilo'utlet 14*. A conduit 16' fromthe engine oil sump, not shown here, leads-t6 a solenoid operatecli two-way valve LB; or the tyiie co'mmonly' employed in the art. Thervalve I8 is nor,- mallyheldby an electromagn'et l9 was to permit the oil to flow into inlet conduit t2 and iiitoathe radiator inlet, .bu-t upon deenergizing thezmag net I9, a spring 23,positiens the valve 11% so that the flew; of ,oil will ,be, diverted to conduit 24,, and h nce. h eng ne- The conduitv A, .whi'ch normallit carriesthe oil tromthegradiator I70 into the conduit 24, containsa One-Wait fihechlalye 2: 1; wh ne. w pe mit. flew the ethro e n y i the. dir c ienz n i ated brine v r; arewi-re asing. 92, cvnstruet d' o some: su t: a l e t r e l ond ctor, emp e s rm nd i ad t a sl llPfi idlhyl h dam? e ers-3L sii siua .q i sfi' E-t e c si .30 are spaceds ciently close asto impede the pas;-

sage of missiles therethrough, including the smallest ammunition generatlly employed airgi s 'e; th v cp ls onta'ct with radiator rcraft fi tem w e in t er a e han n A plunger 38 in the solenoid valve I8 under force of the spring 23 is ad-apted to close a normally open switch 40 upon de-energization of the solenoid I9 and thereby feed current from a source of electrical energy or battery H to a warning light 42 which is located at some point within full view of the operators of the craft.

Referring now to Figure 2, wherein an alternate embodiment of the invention is illustrated, the coils 34 connect to the solenoid I 9 from point A, and to the source of electrical potential 36 from point B, as in the previous embodiment of the invention, but ground return coils 44, not touching the coils 34 nor the radiator II], are Wound so that the casing 30 is composed of coils 34 and ground return coils 44 in alternate sequence. The ground return coils 44 are connected to the solenoid I9 on one end, and suitably grounded as at 46 on the opposite end.

Having thus described the device, in operation, it will now be apparent to those skilled in the art that when a bullet or other missile, such as shrapnel from an aerial bomb or anti-aircraft shell, strikes the radiator II], it will first shatter at least one of the wire coils 34 of the casing 30, thereby immediately shorting out the solenoid I 9 of the valve I8, and thereby actuating the valve to close conduit I2 from conduit I6 and cause the oil to by-pass the now punctured radiator I0, to the engine by means of passage 24. Simultaneously, the plunger 38 will close the switch 40 to energize the warning light 42, thereby apprising the operators of the craft of the dangerous condition.

To further insure positive operation of the device, the distance between the radiator I and the casing 30 is relatively small, so that a hit on the radiator will inevitably cause the portion of the casing struck to ground out the circuit against the radiator which as shown in Figure 1 is grounded at C, thereby rendering the by-pass valve l8 operative. The check valve 28 in conduit I4 obviates the possibility that oil might flow from the conduit 24 into the damaged radiator I0 while the by-pass is operative.

In this manner, the lubricant circulating through the oil system will not be lost through the punctured radiator, and a supply of lubricant will continue being supplied to the engine, which will be adequate for a reasonable period of time, "as heretofore explained.

In the second embodiment of the invention, as illustrated in Figure 2, it will be apparent that by alternating each coil 34 with a ground return coil 44, the by-pass valve I8 and the warning light 42 will be rendered operative if the coils 34 and 44 are brought into contact with one another, since the solenoid I 9 will thereby be grounded out.

This type of circuit negates the possibility that the casing 30 might be shattered, but loose strands of bare wire accidentally in contact with one another could complete the circuit so as to maintain the solenoid I9 energized, and, therefore, prevent the oil from by-passing the radiator, and render the warning device 42 inoperative. There are thus provided means for protecting the oil supply of an engine in the event that the radiator is rendered inoperative by a direct hit, which are light in weight, easy and economical to install and maintain, and yet positive and reliable in operation.

Although only two embodiments of the invention have been illustrated and described, other changes and modifications in form and relative arrangement of parts, which will be apparent to those skilled in the art, may be made without departing from the spirit and scope of the invention.

What is claimed is:

1. In an engine oil system for aircraft, the combination comprising a. radiator including an inlet and an outlet, a transfer valve upstream of said radiator inlet, said transfer valve having an inlet and first and second outlets, an inlet conduit connecting said transfer valve inlet to a source of oil for the engine, a first outlet conduit connecting said first transfer valve outlet to the engine, a second outlet conduit connecting said second transfer valve outlet to said radiator inlet, a solenoid normally energized to affect said transfer valve so as to close said first transfer valve outlet and open said second transfer valve outlet, an outlet line leading from said radiator outlet to the engine, check valve means in the outlet line preventing back flow from the engine to said radiator, a bare wire casing forming a continuous electrical circuit encompassing said radiator, said circuit connected to the solenoid of said transfer valve and to a source of electrical potential, and spring biasing means to operate said transfer valve so as to open said first outlet conduit and close said second outlet conduit upon the interruption of said circuit and the of said solenoid to thereby cause the oil to by-pass said radiator and flow directly to the engine.

2. In an engine oil system for aircraft, the combina circuit including a source of electrical potential, part of said electrical circuit,

trical circuit and being disposed to be broken upon the passage of a missile therethrough, a valve upstream of said radiator, said valve havoutlet conduit to said engine and close said second conduit to said radiator operative upon contact of at least one of said live coils with one of said ground return coils to thereby deenergize said solenoid and prevent flow to said radiator and operate said warning device.

4. In an engine oil system for aircraft, the combination, a radiator including an inlet and an outlet, a valve upstream of said inlet, said valve having an inlet conduit, a first outlet conduit leading to said engine and a second outlet conduit leading to said radiator inlet, a solenoid normally energized to affect said valve so as to close said first conduit and open said second conduit, an outlet line leading from said radiator outlet to said engine, check valve means in the outlet line preventing back flow to said outlet, a bare wire casing comprising alternateh a live coil and a ground return coil adjacent thereto, forming a continuous electrical circuit encompassing said radiator, said circuit connected to the solenoid of said valve and to a source of electrical potential, biasing means to operate said valve so as to open said first outlet conduit and close said second outlet conduit upon contact of at least one of said live coils With one of said ground return coils thereby causing the oil to by-pass said radiator and flow direct to said engine, a plunger on said valve, and a warning light energized by the movement of said plunger to signal the interruption of said circuit by the contact of said valve coil with said return coil.

5. In a protective system for an aircraft engine oil system, the combination comprising a radiator including an inlet and an outlet, a bare single wire casing completely encasing said radiator, said wire forming an electrical circuit and being disposed so as to be broken upon the passage of a missile therethrough, a valve upstream of said radiator inlet, said Valve having an inlet connected to the source of oil for the engine and a first outlet connected to the engine and a second outlet connected to said radiator inlet, spring means biasing said valve to open said first outlet and close said second outlet, a solenoid forming a part of said circuit and operatively associated with said valve, said solenoid being normally energized to move said valve against the bias of said spring means so as to close said first outlet and open said second outlet to permit said valve to pass flow to said radiator inlet, an outlet conduit connecting said radiator outlet to the engine, check valve means in said radiator outlet con..-

duit and preventing flow from the engine to said radiator outlet, and a warning device controlled by the position of said valve, said solenoid being de-energized upon the grounding of said wire against said radiator, said spring means being efiective on the de-energization of said solenoid to move said valve to open said first outlet and close said second outlet to thereby prevent flow to said radiator inlet and to operate said warning device.

6. In a protective system for an aircraft engine oil system, the combination comprising a radiator including an inlet and an outlet, a bare single wire casing completely encasing said radiator, said wire forming an electrical circuit and being disposed so as to be' broken upon the passage of a missile therethrough, a valve upstream of said radiator inlet, said valve means having an inlet connected to the source of oil for the engine and a first outlet connected to the engine and a second outlet connected to said radiator inlet, spring means biasing said valve to open said first outlet and close said second outlet, a solenoid forming a part of said circuit and operatively associated with said valve, said solenoid being normally energized to move said valve against the bias of said spring means to close said first outlet and open said second outlet to permit said valve to pass flow to said radiator inlet, an outlet conduit connecting said radiator outlet to the engine, check valve means in said radiator outlet conduit and preventing flow from the engine to said radiator outlet, and a warning device controlled by the position of said valve, said solenoid being de-energized upon the breaking of said Wire whereby said circuit is interrupted and said spring means being effective on the de-energization of said solenoid to move said valve to close said second outlet and open said first outlet to prevent flow to said radiator inlet and to operate said warning device.

WALTER D. TEAGUE, JR.

References Cited in the file of this patent UNITED STATES PATENTS

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